A composite honeycomb winding core mold and a preparation method thereof

Abstract

This invention discloses a composite material honeycomb winding mandrel and its preparation method, including a composite material honeycomb winding mandrel and its preparation method. The composite material honeycomb winding mandrel includes a mandrel with a cylindrical winding layer on its exterior and a honeycomb sandwich layer between the mandrel and the cylindrical winding layer. A dummy front end is located on the left side of the mandrel, and a dummy rear end is located on the right side of the mandrel. Both the dummy front and rear ends are locked with nuts. The mandrel includes a left end, a right end, and a mandrel cylindrical segment. The left and right ends are respectively located at both ends of the mandrel cylindrical segment. Both ends of the mandrel have steps for positioning the dummy front end, and both ends of the mandrel also have external threads that match the dummy front end. Compared with the prior art, the composite material honeycomb winding mandrel and its preparation method of this invention can largely ensure the strength and stiffness of the mandrel, reduce deflection deformation, and further achieve the lightweighting of the mandrel.

Description

Technical Field

[0001] This invention belongs to the field of core mold technology, specifically relating to a composite material honeycomb winding core mold and its preparation method. Background Technology

[0002] Missile launch tubes are specialized devices for holding and launching missiles, serving functions such as orientation, support, erection, temperature control, missile storage, and launch. Traditional missile launch tubes use metal materials, resulting in heavy weight and high energy consumption during transportation. Composite materials, due to their superior properties such as low specific gravity, high specific strength, and high specific modulus, have been widely used in missile launch tube manufacturing.

[0003] Composite material launch tubes are typically formed using a winding process, and the mandrel used in this process is usually made of metal. Metal mandrels are characterized by high strength, but they are also heavy, difficult to assemble and disassemble, and have poor assembly precision. In addition, because launch tubes generally have a large length-to-diameter ratio, metal mandrels have large deflection and poor rigidity.

[0004] The information disclosed in this background section is intended only to enhance the understanding of the overall background of the invention and should not be construed as an admission or in any way implying that the information constitutes prior art known to those skilled in the art. Summary of the Invention

[0005] The purpose of this invention is to provide a composite honeycomb winding mandrel and its preparation method, which can largely guarantee the strength and stiffness of the mandrel, reduce deflection deformation, and further achieve the lightweighting of the mandrel.

[0006] To achieve the above objectives, a specific embodiment of the present invention provides the following technical solution:

[0007] A composite material honeycomb winding mandrel includes a mandrel, a cylindrical winding layer is provided on the outside of the mandrel, a honeycomb sandwich layer is provided between the mandrel and the cylindrical winding layer, and a dummy front end and a dummy rear end are respectively provided at both ends of the mandrel, and the dummy front end and the dummy rear end are locked by nuts.

[0008] In one or more embodiments of the present invention, the mandrel includes a left end, a right end, and a mandrel cylindrical section, wherein the left end and the right end are respectively disposed at both ends of the mandrel cylindrical section.

[0009] In one or more embodiments of the present invention, both ends of the mandrel are provided with steps for positioning the dummy front end cap, and both ends of the mandrel are also provided with external threads that match the dummy front end cap, and the nut and the external threads are threaded connections.

[0010] In one or more embodiments of the present invention, a release layer is further provided on the outer surface of the mandrel section.

[0011] In one or more embodiments of the present invention, the release layer is a polytetrafluoroethylene release fabric.

[0012] In one or more embodiments of the present invention, the honeycomb sandwich layer includes a glass fiber composite winding layer, a glass fiber cloth composite filling layer, and a honeycomb structure, wherein adjacent honeycomb structures are spliced ​​together, and the glass fiber cloth composite filling layer is used to fill the splice of adjacent honeycomb structures.

[0013] In one or more embodiments of the present invention, the dummy front end and dummy rear end are both metal end caps or acrylic end caps.

[0014] In one or more embodiments of the present invention, the outer diameter of the mandrel section is greater than the outer diameter of the left end and the right end.

[0015] A method for preparing a composite honeycomb winding mandrel includes the following steps:

[0016] S1. Making the mandrel:

[0017] First, prepare the left end, right end, and mandrel section. Weld the left end and right end to both ends of the mandrel section respectively. Then, use a machine tool to cut external threads on the left end and right end to obtain the mandrel.

[0018] S2. Fabricating the honeycomb sandwich layer:

[0019] Connect the mandrel obtained in step S1 to the winding equipment, lay a release layer on the surface of the mandrel cylinder section, then wind the glass fiber composite material winding layer in a circumferential direction, and then lay a honeycomb structure. The splicing of the honeycomb structures is filled with a glass fiber cloth composite material filling layer to complete the single-layer honeycomb layup. Repeat the above layup action according to the diameter of the launch tube to N layers of honeycomb layup to obtain a honeycomb sandwich layer.

[0020] S3. Fabricate the cylindrical winding layer:

[0021] After the honeycomb sandwich layer is prepared in step S2, pre-impregnated glass fiber is wound circumferentially on the outer surface of the mandrel section, and glass fiber cloth is laid between the multiple circumferential winding layers. After the winding is completed, the mold is cured in an oven to obtain the section winding layer.

[0022] S4. Head assembly:

[0023] The dummy front end and dummy rear end are installed on both sides of the mandrel section, and the dummy front end and dummy rear end are fixed with nuts. After the dummy front end and dummy rear end are assembled, a release layer is laid on the outer surface of the winding layer of the mandrel section.

[0024] In one or more embodiments of the present invention, the glass fiber composite winding layer is made of circumferentially wound glass fiber and glass fiber cloth pre-impregnated with resin.

[0025] Compared with the prior art, the composite honeycomb winding mandrel and its preparation method of the present invention can largely guarantee the strength and stiffness of the mandrel, reduce deflection deformation, and further realize the lightweighting of the mandrel. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0027] Figure 1 This is a schematic diagram of the structure of a composite honeycomb winding mandrel in one embodiment of the present invention;

[0028] Figure 2 This is a cross-section of a composite honeycomb winding mandrel according to an embodiment of the present invention. Figure 1 ;

[0029] Figure 3 This is a cross-section of a composite honeycomb winding mandrel according to an embodiment of the present invention. Figure 2 ;

[0030] Figure 4 This is a flowchart illustrating a method for preparing a composite honeycomb winding mandrel according to an embodiment of the present invention.

[0031] Explanation of key figure labels:

[0032] 1. Left end; 2. Right end; 3. Mandrel section; 4. Nut; 5. Demolding layer; 6. False front end; 7. False rear end; 8. Honeycomb sandwich layer; 81. Glass fiber composite winding layer; 82. Glass fiber cloth composite filling layer; 83. Honeycomb structure; 9. Section winding layer. Detailed Implementation

[0033] To enable those skilled in the art to better understand the technical solutions of this invention, the technical solutions of the embodiments of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this invention, and not all embodiments. Based on the embodiments of this invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of this invention.

[0034] like Figures 1-2 As shown, a composite honeycomb winding mandrel in one embodiment of the present invention includes a mandrel located inside the mandrel, which provides support for other components. A cylindrical winding layer 9 is also provided on the outer side of the mandrel, serving as the main load-bearing structure. A honeycomb sandwich layer 8 is also provided between the left end 1 and the cylindrical winding layer 9. A dummy front end cap 6 and a dummy rear end cap 7 are respectively fitted onto the left end 1 and the right end 2, both secured by nuts 4.

[0035] The cylindrical winding layer 9 is a composite material made of glass fiber pre-impregnated resin, with a large thickness, providing strength and rigidity support during the winding of the launch tube. A release layer 5, which is made of polytetrafluoroethylene release fabric, is provided on the outer surface of the cylindrical winding layer 9.

[0036] The mandrel is made of metal. It comprises a left end 1, a right end 2, and a mandrel cylindrical section 3. The left end 1 and right end 2 are welded to both ends of the mandrel cylindrical section 3. This welding ensures the stability of the connection between the left end 1, right end 2, and mandrel cylindrical section 3. The outer diameter of the mandrel cylindrical section 3 must be larger than the outer diameters of both the left end 1 and right end 2 to ensure that both ends can be assembled into the winding equipment. Both ends of the mandrel have steps and threads. The steps are used for positioning and installing the dummy front end 6 and dummy rear end 7, while the threads are used for threaded connection with the nuts 4. The nuts 4 then secure the dummy front end 6 and dummy rear end 7.

[0037] The front dummy head 6 and the rear dummy head 7 are both made of metal or acrylic materials. Specifically, the metal dummy head 6 and the rear dummy head 7 are both metal or acrylic heads. The metal heads can be steel heads. Metal heads are not easily worn during use and can be used for a long time. The front dummy head 6 and the rear dummy head 7 provide winding line support for the winding launch tube.

[0038] Furthermore, threads are formed on the outer surfaces of the left end 1 and the right end 2, meaning that the two nuts 4 are threadedly connected to the left end 1 and the right end 2 respectively.

[0039] like Figures 1-2 As shown, a release layer 5 is provided on the outer surface of the mandrel section 3, and the release layer 5 is a polytetrafluoroethylene release cloth.

[0040] like Figure 3 As shown, the honeycomb sandwich layer 8 is made of glass fiber composite material and multiple multi-layer honeycomb structures 83. The joints between honeycomb structures 83 in a single layer and between each honeycomb structure 83 are filled with glass fiber composite material. That is, a glass fiber cloth composite material filling layer 82 is provided at the joints between honeycomb structures 83 in a single layer and between each honeycomb structure 83. The glass fiber cloth composite material filling layer 82 plays a role in rigidity support.

[0041] like Figure 4 As shown, a method for preparing a composite honeycomb winding mandrel is as follows:

[0042] S1. First, prepare the left end 1, the right end 2, and the mandrel section 3. The left end 1 and the right end 2 are both made of metal steel rings, and the mandrel section 3 is made of seamless metal steel pipe. The left end 1 and the right end 2 are welded to both ends of the mandrel section 3 by welding. Then, the outer walls of the mandrel section 3, the left end 1, and the right end 2 are opened with external threads using a machine tool to obtain the mandrel.

[0043] S2. Fabricate the honeycomb sandwich layer 8. Connect the mandrel prepared in step S1 to the winding equipment. Lay a release layer 5 on the surface of the mandrel cylinder section 3, then circumferentially wind the glass fiber composite material winding layer 81, and then lay a honeycomb structure 83. The joints between honeycomb structures 83 are filled with a glass fiber cloth composite material filling layer 82. When laying a single layer of honeycomb structure 83, circumferential fiber winding is used for fixation.

[0044] After the honeycomb layer is laid up, a second layer of glass fiber composite material 81 is wound. This layer of composite material is made of circumferentially wound glass fiber and glass fiber cloth pre-impregnated with resin. After winding, a second layer of honeycomb structure 83 is laid up, with the same laying scheme as the first layer, and so on up to the nth layer of honeycomb structure 83. If the diameter of the launch tube is large, a pre-curing process is added in the middle. An oven is used to pre-cur the mold, and after pre-curing, the (n+1)th layer of honeycomb is laid up.

[0045] S3. Fabrication of the winding layer 9: After the honeycomb sandwich layer 8 is prepared, pre-impregnated resin-coated glass fiber is wound circumferentially around the outer surface of the mandrel segment 3. Simultaneously, glass fiber cloth is laid between the multiple circumferential winding layers to ensure the axial stiffness of the winding layer 9. After winding, the mold is cured in an oven. After curing, the excess material on the outer surface of the winding layer 9 is machined using a machine tool to achieve the required dimensional accuracy.

[0046] S4. Use a machine tool to machine the dummy front head 6 and dummy rear head 7 to meet the design requirements.

[0047] S5. Head assembly: Install the dummy front head 6 and dummy rear head 7 on the left and right sides of the mandrel cylinder section 3 respectively, and fix both ends with nuts 4. After the head assembly is completed, lay the release layer 5 on the outer surface of the cylinder section winding layer 9.

[0048] This invention relates to a wound mandrel constructed from glass fiber composite material and a honeycomb sandwich structure, resulting in a weight reduction of over 50% compared to metal mandrels. It prevents deflection deformation caused by the mandrel's own weight due to its large aspect ratio. The use of glass fiber composite material with high specific strength and high specific stiffness significantly improves its strength and stiffness compared to metal mandrels. The outer diameter of the 9-layer winding section is ensured by integral machining, resulting in high dimensional accuracy. The structure has fewer parts, simplifying disassembly and installation.

[0049] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0050] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A composite honeycomb-wrapped core former, characterized by, Includes a mandrel, the mandrel is provided with a cylindrical winding layer on the outside, and a honeycomb sandwich layer is provided between the mandrel and the cylindrical winding layer. A false front end is located on the left side of the mandrel, and a false rear end is located on the right side of the mandrel. Both the false front end and the false rear end are locked with nuts. The honeycomb sandwich layer includes a glass fiber composite winding layer, a glass fiber cloth composite filling layer, and a honeycomb structure. Adjacent honeycomb structures are spliced ​​together, and the glass fiber cloth composite filling layer is used to fill the splice joints of adjacent honeycomb structures.

2. A composite honeycomb wound core former according to claim 1, wherein, The mandrel includes a left end, a right end, and a mandrel cylindrical section, with the left end and right end respectively located at both ends of the mandrel cylindrical section.

3. A composite material honeycomb winding mandrel according to claim 1 or 2, characterized in that, Both ends of the mandrel are provided with steps for positioning the dummy front end cap, and both ends of the mandrel are also provided with external threads that match the dummy front end cap. The nut and the external threads are threaded connections.

4. A composite material honeycomb winding mandrel according to claim 3, characterized in that, A release layer is also provided on the outer surface of the mandrel section.

5. A composite material honeycomb winding mandrel according to claim 4, characterized in that, The release layer is a polytetrafluoroethylene release fabric.

6. A composite material honeycomb winding mandrel according to claim 1, characterized in that, Both the dummy front end and the dummy rear end are metal or acrylic end caps.

7. A composite material honeycomb winding mandrel according to claim 1, characterized in that, The outer diameter of each mandrel section is larger than the outer diameter of the left and right ends.

8. A method for preparing a composite material honeycomb winding mandrel, characterized in that, Includes the following steps: S1. Making the mandrel: First, prepare the left end, right end, and mandrel section. Weld the left end and right end to both ends of the mandrel section respectively. Then, use a machine tool to cut external threads on the left end and right end to obtain the mandrel. S2. Fabricating the honeycomb sandwich layer: Connect the mandrel obtained in step S1 to the winding equipment, lay a release layer on the surface of the mandrel cylinder section, then wind the glass fiber composite material winding layer in a circumferential direction, and then lay a honeycomb structure. The splicing of the honeycomb structures is filled with a glass fiber cloth composite material filling layer to complete the single-layer honeycomb layup. Repeat the above layup action according to the diameter of the launch tube to N layers of honeycomb layup to obtain a honeycomb sandwich layer. S3. Fabricate the cylindrical winding layer: After the honeycomb sandwich layer is prepared in step S2, pre-impregnated glass fiber is wound circumferentially on the outer surface of the mandrel section, and glass fiber cloth is laid between the multiple circumferential winding layers. After the winding is completed, the mold is cured in an oven to obtain the section winding layer. S4. Head assembly: The dummy front end and dummy rear end are installed on both sides of the mandrel section, and the dummy front end and dummy rear end are fixed with nuts. After the dummy front end and dummy rear end are assembled, a release layer is laid on the outer surface of the winding layer of the mandrel section.

9. The method for preparing a composite honeycomb winding mandrel according to claim 8, characterized in that, The glass fiber composite winding layer is made of circumferentially wound glass fiber and glass fiber cloth pre-impregnated with resin.

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